| 精确动力学模型下的火星探测轨道设计 |
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| 引用本文： | 陈杨,赵国强,宝音贺西,李俊峰.精确动力学模型下的火星探测轨道设计[J].中国空间科学技术,2011,31(1):8-15. |
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| 作者姓名： | 陈杨 赵国强 宝音贺西 李俊峰 |
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| 作者单位： | （清华大学航天航空学院，北京 100084) |
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| 摘 要： | 首先在二体意义下采用粒子群优化算法（PSO）求解Lambert问题，确定发射窗口和二体地火转移轨道。使用圆锥曲线拼接法设计地心停泊轨道、逃逸轨道，并作为轨道精确设计的初值，以建立在火星的B平面参数和地火转移时间为约束，在精确动力学模型下进行微分迭代修正，最终得到满足约束的精确轨道。将设计轨道在STK软件中仿真，结果吻合。
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| 关 键 词： | 二体问题 微分迭代 轨道设计 精确动力学模型 火星探测器 仿真 |
Orbit Design for Mars Exploration by the Accurate Dynamic Model |
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| Chen Yang,Zhao Guoqiang,Baoyin Hexi,Li Junfeng.Orbit Design for Mars Exploration by the Accurate Dynamic Model[J].Chinese Space Science and Technology,2011,31(1):8-15. |
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| Authors: | Chen Yang Zhao Guoqiang Baoyin Hexi Li Junfeng |
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| Institution: | (School of Aerospace Engineering, Tsinghua University, Beijing 100084) |
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| Abstract: | The precision orbit design for Mars exploration by the accurate dynamic model was studied. The launch window and trans-Mars orbit was determined through the partical swarm optimization (PSO) algorithm within the heliocentric two-body restriction. The patched conics method was introduced to design the earth-centred parking orbit and departure hyperbolic orbit. The solution of two-body Lambert problem was input as initial value for precision orbit design, and the preliminary orbit was corrected with the restrictions of the Mars B-plane parameters and flight time by the accurate dynamic model. Finally the designed orbit was simulated with the STK softwares. |
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| Keywords: | Two-body problem Differential iteration Orbit design Precision dynamic model Mars probe Simulation |
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